Basic experiment on a supersonic vortex flow around a missile body

Pagan, Didier; Molton, Pascal

doi:10.2514/6.1991-287

Cited by 6 publications

(3 citation statements)

References 1 publication

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“…This test demonstrated that the intensity of the vortex flow is sensitive to the laminar or turbulent nature of the boundary layers. First experiments were carried out with Re=0.16•10 6 , by [6]. This permitted to switch from the laminar to turbulent boundary layer when transition was free or triggered on the body apex.…”

Section: Resultsmentioning

confidence: 99%

Review of the Spalart-Allmaras turbulence model and its modifications to three-dimensional supersonic configurations

Kostić¹

2015

Sci Tech Rev

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The Spalart-Allmaras (SA) model is a turbulence model for modeling different types of turbulent flows, especially in aerodynamics. Until 1992, when it was published by Spalart and Allmaras, there had been modified different terms of the governing equation of this model (prediction, diffusion and destruction). In this literature review, one can go through the details of the governing equation of this model and the role of each term and reasoning behind it. The model is implemented in three-dimensional compressible supersonic flows, and validated for two different configurations: a ballistic missile and a cruciform missile simulations show the ability of the method to snap the interaction between the fuselage vortices and the winglets

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Section: Resultsmentioning

confidence: 99%

Review of the Spalart-Allmaras turbulence model and its modifications to three-dimensional supersonic configurations

Kostić¹

2015

Sci Tech Rev

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“…Aside from the control system responsible for maneuvering the projectile, the aerodynamics of such configurations at high speeds are still complex due to strong cross-flow influences and flow separation. 3,4,5 The work documented herein is part of an international collaborative effort specifically dealing with high-speed weapon integration. Under this collaboration, complementary technical tasks are performed to provide a greater overall understanding 2 of the technology.…”

Section: Introductionmentioning

confidence: 99%

Comparison of numerical methods for an elliptic section projectile

Forsythe

2001

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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This paper presents a comparison of several computational fluid dynamics codes applied to a power-law elliptic cross-section projectile at Mach 4.0. Experimental data is used primarily as a basis of comparison, supplemented by limited free flight results. Four codes were used-CHASM, CFD++, Cobalt 60 , and ZNSFLOW. The methods used included the solution of the parabolized and full Navier Stokes equations on structured and unstructured grids using several different turbulence models. All codes were seen to predict normal forces and moments to within a few percent. Discrepancies were noticed in the center of pressure predictions for one code. Only the full Navier Stokes codes could solve for free flight axial force because of the need to solve for base drag. The predictions of axial force compared to the wind tunnel were within about 10%. Larger differences were seen at free flight conditions. Computation times were discussed with the parabolized Navier Stokes having a clear advantage.

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“…4a. Similar primary vortex pairs have been noted experimentally on a tangent-ogive cylinder body with elliptic cross section by Ward and Katz, 23 on a missile body by Pagan and Molton, 24 and computationally on a hemisphere-cylinder body by Ying et al 25 Figure 5 shows computed surface flow patterns on the tangent-ogive cylinder body which were obtained by using the NSS and F3D codes. These patterns were constructed by computing particle paths that are constrained to a surface of grid points one point above the body in the body-normal direction.…”

Section: Comparison Of Computation and Experimentsmentioning

confidence: 66%

Comparison of two Navier-Stokes codes for simulating high-incidence vortical flow

Chaderjian¹

1993

Journal of Aircraft

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Computations from two Navier-Stokes codes, NSS and F3D, are presented for a tangent-ogive cylinder body at high angle of attack. Features of this steady flow include a pair of primary vortices on the leeward side of the body, as well as secondary vortices. The topological and physical plausibility of this vortical structure is discussed. The accuracy of these codes are assessed by comparison of the numerical solutions with experimental data. The effects of turbulence model, numerical dissipation, and grid refinement are presented. The overall efficiency of these codes are also assessed by examining their convergence rates, computational time per time step, and maximum allowable time step for time-accurate computations. Overall, the numerical results from both codes compared equally well with experimental data, however, the NSS code was found to be significantly more efficient than the F3D code.

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Basic experiment on a supersonic vortex flow around a missile body

Cited by 6 publications

References 1 publication

Review of the Spalart-Allmaras turbulence model and its modifications to three-dimensional supersonic configurations

Review of the Spalart-Allmaras turbulence model and its modifications to three-dimensional supersonic configurations

Comparison of numerical methods for an elliptic section projectile

Comparison of two Navier-Stokes codes for simulating high-incidence vortical flow

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